Catalytic surface effects experiment on the Space Shuttle

Stewart, David A.; Rakich, J. V.; Lanfranco, M. J.

doi:10.2514/6.1981-1143

Cited by 53 publications

(35 citation statements)

References 6 publications

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“…It should be noted that several of the tiles on all ights particularly STS 5 had catalytically enhanced surfaces. 39 However, as discussed in Ref. 39, the area of in uence appears to be very localized high heating rates.…”

Section: Surface Pressuresmentioning

confidence: 99%

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Characteristics of the Shuttle Orbiter leeside flow during a re-entry condition

William

James

1994

Journal of Spacecraft and Rockets

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A study of the leeside ow c haracteristics of the Shuttle Orbiter is presented for a reentry ight condition. The ow is computed using a point-implicit, nite-volume scheme known as the Langley Aerothermodynamic U p wind Relaxation Algorithm LAURA.LAURA is a second-order accurate, laminar NavierStokes solver, incorporating nite-rate chemistry with a radiative equilibrium wall temperature distribution and nite-rate wall catalysis. The resulting computational solution is analyzed in terms of salient o w features and the surface quantities are compared with ight data. NomenclatureAcronyms AFRSI Advanced exible reusable surface insulation DFI Developmental ight instrumentation LAURA Langley aerothermodynamic upwind relaxation algorithm OMS Orbital maneuvering system PNS Parabolized Navier-Stokes RCC Reinforced carbon-carbon RCG Reaction cured gas RCS Reaction control system SILTS Shuttle infrared leeside temperature sensing STEIN Supersonic hypersonic three-dimensional external inviscid ow STS Space transportation system

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Section: Surface Pressuresmentioning

confidence: 99%

“…39 However, as discussed in Ref. 39, the area of in uence appears to be very localized high heating rates. data, and once past X L=0.55 not even the trend in heating is captured correctly.…”

Section: Surface Pressuresmentioning

confidence: 99%

Characteristics of the Shuttle Orbiter leeside flow during a re-entry condition

William

James

1994

Journal of Spacecraft and Rockets

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“…These cases are modeled using a five species (N, O, N 2 , O 2 , and NO) chemical nonequilibrium, non-ionizing air chemistry model 6 . A radiative equilibrium wall temperature boundary condition is set at the surface, and Reaction Cured Glass (RCG) catalycity 7 are applied at the surface of the Orbiter tiles and the BLT protuberance. Both codes have been used extensively to predict aerothermal environments for the Space Shuttle as well as other Earth entry vehicles (e.g., Fire-II 8 , Apollo 9,10 , and Genesis 11,12 ).…”

Section: Computational Methodologymentioning

confidence: 99%

Numerical Simulations of the Boundary Layer Transition Flight Experiment

Tang

Trumble

Campbell

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…The two-equation temperature-dependent nitrogen and oxygen recombination coefficients for RCG, 6 C742, 7 and RCC (C-CAT), 25 as well as the twoequation temperature-dependent air recombination coefficient model for RCG 25 are plotted vs. temperature in Figure 3(a). Although a four-equation model for RCG partially catalytic recombination coefficients is available, the two-equation model was used in this analysis for consistency with previous analyses.…”

Section: Catalytic Recombination Coefficientsmentioning

confidence: 99%